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公开(公告)号：US10323541B2
公开(公告)日：2019-06-18
申请号：US15459125
申请日：2017-03-15
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Shivakumar Basavanna , Jacob Patrick Miller , Charles Andrew Corman , Mark Leonard Hopper
IPC: F01D25/16 , F16C35/04 , F16C35/067 , F04D29/52 , F04D29/32 , F04D29/059 , F01D21/04 , F01D21/08 , F02C7/06
Abstract: A housing for retention of the outer race of a bearing of a gas turbine engine includes an arrangement of spring fingers that yields a lightweight housing capable of withstanding very high radial loads combined with very high torsional windup and axial thrust load. Controlled circumferential gaps on both sides of each spring finger limit the deflection and self-arrest the distortion of the housing. The spring fingers define at least one side edge that extends at an angle relative to the axial direction. An axial gap is created on the aft end by a portion of the spring finger beam structure that opposes an axial face of the housing and limits the axial distortion. A radial gap created between interface hardware of the housing and the inner retention housing also acts to retain the spring finger housing under load in a radial direction.
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公开(公告)号：US20180266275A1
公开(公告)日：2018-09-20
申请号：US15459125
申请日：2017-03-15
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Shivakumar Basavanna , Jacob Patrick Miller , Charles Andrew Corman , Mark Leonard Hopper
IPC: F01D25/16 , F16C35/04 , F16C35/067 , F01D5/02 , F01D25/24 , F04D29/52 , F04D29/32 , F04D29/053 , F04D29/059 , F02K3/06
CPC classification number: F01D25/164 , F01D21/045 , F01D21/08 , F02C7/06 , F04D29/059 , F04D29/321 , F04D29/522 , F05D2260/30 , F16C35/042 , F16C35/067 , F16C2360/24 , Y02T50/671
Abstract: A housing for retention of the outer race of a bearing of a gas turbine engine includes an arrangement of spring fingers that yields a lightweight housing capable of withstanding very high radial loads combined with very high torsional windup and axial thrust load. Controlled circumferential gaps on both sides of each spring finger limit the deflection and self-arrest the distortion of the housing. The spring fingers define at least one side edge that extends at an angle relative to the axial direction. An axial gap is created on the aft end by a portion of the spring finger beam structure that opposes an axial face of the housing and limits the axial distortion. A radial gap created between interface hardware of the housing and the inner retention housing also acts to retain the spring finger housing under load in a radial direction.
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Patent Agency Ranking
公开(公告)号：US10711693B2
公开(公告)日：2020-07-14
申请号：US15647380
申请日：2017-07-12
Applicant: General Electric Company
Abstract: A turbine engine has a core with a compressor, combustor, and turbine sections in axial flow arrangement and with corresponding rotating elements mounted to a shaft defining engine rotor elements. The turbine engine has a rotary driver operably coupled to the engine rotor elements. The turbine engine has at least one thermoelectric generator in thermal communication with the core and in electrical communication with the rotary driver to provide power to the rotary driver to turn the engine rotor elements.
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公开(公告)号：US20180347389A1
公开(公告)日：2018-12-06
申请号：US15609464
申请日：2017-05-31
Applicant: General Electric Company
Inventor： Brian Joseph Prenger , John David Bibler , Mark Leonard Hopper
CPC classification number: F04D29/083 , F01D11/003 , F01D11/025
Abstract: Aspirating face seal between high and low pressure regions of turbomachine between rotatable and non-rotatable members of turbomachine includes gas bearing rotatable and non-rotatable face surfaces, starter tooth mounted on the rotatable member operable to sealingly engage abradable starter seal land on the non-rotatable member, and annular pocket in an abradable coating or other abradable material of starter seal land. Abradable material may be in radially inwardly facing groove extending into non-rotatable member. Pocket may extend radially outwardly from a cylindrical radially outer abradable surface to pocket bottom which includes thin abradable material layer groove surface along the non-rotatable member. Pocket may extend axially aftwardly from annular forward groove side surface into abradable coating. Pocket may be bounded axially by abradable material. Pocket may be tapered having taper decreasing axially aftwardly away from annular forward groove side surface.
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公开(公告)号：US11454134B2
公开(公告)日：2022-09-27
申请号：US16985392
申请日：2020-08-05
Applicant: General Electric Company
Inventor： Mark Leonard Hopper , Justin Adam Masters , Jacob Patrick Miller , Roger Lee Doughty
Abstract: A gas turbine engine having a damping system that includes features for optimizing the damping response to vibrational loads on a rotary component for a wide range of operational conditions is provided. In one aspect, the damping system includes a damper control valve. The damper control valve receives working fluid from a working fluid supply and has a valve plunger movable between a first position and a second position. When the valve plunger is in the first position, the damper control valve permits working fluid to flow to a first damper associated with a first bearing coupled with the rotary component and to a second damper associated with a second bearing coupled with the rotary component. When the valve plunger is in the second position, the damper control valve permits working fluid to flow to the first damper but not the second damper.
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公开(公告)号：US10329938B2
公开(公告)日：2019-06-25
申请号：US15609464
申请日：2017-05-31
Applicant: General Electric Company
Inventor： Brian Joseph Prenger , John David Bibler , Mark Leonard Hopper
Abstract: Aspirating face seal between high and low pressure regions of turbomachine between rotatable and non-rotatable members of turbomachine includes gas bearing rotatable and non-rotatable face surfaces, starter tooth mounted on the rotatable member operable to sealingly engage abradable starter seal land on the non-rotatable member, and annular pocket in an abradable coating or other abradable material of starter seal land. Abradable material may be in radially inwardly facing groove extending into non-rotatable member. Pocket may extend radially outwardly from a cylindrical radially outer abradable surface to pocket bottom which includes thin abradable material layer groove surface along the non-rotatable member. Pocket may extend axially aftwardly from annular forward groove side surface into abradable coating. Pocket may be bounded axially by abradable material. Pocket may be tapered having taper decreasing axially aftwardly away from annular forward groove side surface.
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公开(公告)号：US20190017438A1
公开(公告)日：2019-01-17
申请号：US15647380
申请日：2017-07-12
Applicant: General Electric Company
CPC classification number: F02C6/18 , F01D15/10 , F01D25/36 , F02C3/04 , F02C7/32 , F02C7/36 , F05D2260/4031 , H01L35/30
Abstract: A turbine engine has a core with a compressor, combustor, and turbine sections in axial flow arrangement and with corresponding rotating elements mounted to a shaft defining engine rotor elements. The turbine engine has a rotary driver operably coupled to the engine rotor elements. The turbine engine has at least one thermoelectric generator in thermal communication with the core and in electrical communication with the rotary driver to provide power to the rotary driver to turn the engine rotor elements.
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